80 FR 61720 - Airworthiness Directives; General Electric Company Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 198 (October 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 198 (October 14, 2015)
| Page Range | 61720-61722 | |
| FR Document | 2015-25719 |
[Federal Register Volume 80, Number 198 (Wednesday, October 14, 2015)] [Rules and Regulations] [Pages 61720-61722] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-25719] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD; Amendment 39-18288; AD 2015-20-09] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding airworthiness directives (AD) 2001-18-06 and AD 2008-22-16, for all General Electric Company (GE) CT58 turboshaft engines. AD 2001-18-06 and AD 2008-22-16 required recalculating the lives of life-limited rotating parts using a repetitive heavy-lift (RHL) multiplying factor and removal from service of parts that exceed the recalculated cyclic or hourly life limit. This new AD would consolidate AD 2001-18-06 and AD 2008-22-16, and further reduce the life capability of certain parts. This AD was prompted by recalculation of life for parts installed on engines used in Utility operations, and a reduced life for compressor spools in all operations. We are issuing this AD to prevent failure of life-limited rotating parts, uncontained part release, damage to the engine, and damage to the aircraft. DATES: This AD is effective November 18, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 18, 2015. ADDRESSES: For service information identified in this proposed AD, contact General Electric Company, GE Aviation, Room 285, One Neumann Way, Cincinnati, OH, 45215; phone: 513-552-3272; email: [[Page 61721]] ge.com">[email protected]ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2008- 0808; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2001-18-06, Amendment 39-12432 (66 FR 47575, September 13, 2001, (``AD 2001-18-06'') and AD 2008-22-16, Amendment 39-15712 (73 FR 63629, October 27, 2008, (``AD 2008-22-16''). AD 2001- 18-06 and AD 2008-22-16 applied to certain GE CT58 turboshaft engines. The NPRM published in the Federal Register on May 1, 2015 (80 FR 24852). The NPRM was prompted by GE updating the life limits of compressor spools. GE also updated the calculation method for the life consumption of compressor spools and of life-limited rotating parts flown in Utility operations. This update resulted in generally reduced lives for compressor spools and all other life-limited parts used in Utility operations. The NPRM proposed to consolidate AD 2001-18-06 and AD 2008-22-16, and further reduce the life capability of certain parts. We are issuing this AD to prevent failure of life-limited rotating parts, uncontained part release, damage to the engine, and damage to the aircraft. Related Service Information Under 1 CFR Part 51 We reviewed GE CT58 Alert Service Bulletin (ASB) No. SB 72-A0162, Revision 16, dated January 7, 2015. The service information describes procedures for calculating life limits for the affected life-limited rotating parts. This service information is reasonably available because the interested parties have access to it through their normal course of business or see ADDRESSES for other ways to access this service information. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request New Method for Determining Reduced Life Limits AAR Airlift Group (AAR) requested replacement of the current method for determining reduced life limits because current limits do not agree with operators field experience. AAR independent testing revealed that expired critical rotating parts showed no fatigue cracks. We disagree. FAA-approved life limits for rotating parts are specified to prevent fatigue crack initiation, using conservative analytical margins. The number of parts that AAR had inspected would not be sufficient to show a likelihood of part cracking consistent with FAA regulatory guidelines for rotating part life limits. We did not change this AD. Request Reassessment of Cost Impact AAR disagrees that the NPRM has minimal impact on their company. AAR stated that their cost per flight would increase and company revenue would be reduced. We agree that this AD will impose an economic impact to operators. How an operator absorbs or passes on the cost is left to the operator to determine. We did not change this AD. Clarification Requirements Since we issued the proposed AD, we discovered that ASB formatting discrepancies exist due to documentation changes implemented by GE. We changed paragraphs (e)(2), (e)(3), and (e)(4) to reflect the correct SB paragraph numbers. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD will affect about 60 engines installed on aircraft of U.S. registry. The average pro-rated cost of the life- limited rotating parts is $20,000. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $8,715,000. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, [[Page 61722]] the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by: 0 a. Removing airworthiness directives (AD) 2001-18-06, Amendment 39- 12432 (66 FR 47575, September 13, 2001) (``AD 2001-18-06''); and AD 2008-22-16, Amendment 39-15712 (73 FR 63629, October 27, 2008) (``AD 2008-22-16''), and 0 b. Adding the following new AD: 2015-20-09 General Electric Company: Amendment 39-18288; Docket No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD. (a) Effective Date This AD is effective November 18, 2015. (b) Affected ADs This AD replaces AD 2001-18-06 and AD 2008-22-16. (c) Applicability This AD applies to all General Electric Company (GE) CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, and CT58-140-2 turboshaft engines. (d) Unsafe Condition This AD was prompted by recalculation of life for parts installed on engines used in Utility operations, and a reduced life for compressor spools in all operations. We are issuing this AD to prevent failure of life-limited rotating parts, uncontained part release, damage to the engine, and damage to the aircraft. (e) Compliance Do the actions required by this AD, unless already done. (1) Calculating Cyclic Life Consumption Re-calculate the cycles-since-new for all compressor spools, and for life-limited rotating parts other than compressor spools used in Utility operations. Use paragraphs 3.A.(1) and 3.B.(1) in the Accomplishment Instructions of GE CT58 Alert Service Bulletin (ASB) No. SB 72-A0162, Revision 16, dated January 7, 2015, to perform the calculations. (2) Removal of Compressor Spools After the effective date of this AD, remove compressor spools, part numbers (P/Ns) 5124T94G02, 6010T57G04, 6010T57G07, and 6010T57G08 from service, before reaching the life limits specified in paragraph 4.A., Appendix A, in GE CT58 ASB No. SB 72-A0162, Revision 16, dated January 7, 2015, as re-calculated per paragraph (e)(1) of this AD. (3) Removal of Rotating Parts Used in Utility Operations Other Than Compressor Spools After the effective date of this AD, remove from service any life-limited rotating part used in Utility operations, other than the compressor spools with P/Ns listed in paragraph (e)(2) of this AD, that exceeds its life limit as re-calculated per paragraph (e)(1) of this AD. Use Tables I, II, III, and IV in paragraphs 3.D. through 3.G. in the Accomplishment Instructions in GE CT58 ASB No. SB 72-A0162, Revision 16, dated January 7, 2015, and paragraph 4.D., Appendix A of this GE CT58 ASB, to determine when to remove these parts. (4) Removal of Rotating Parts Not Used in Utility Operations Other Than Compressor Spools After the effective date of this AD, remove from service any life-limited rotating part not used in Utility operations, other than the compressor spools with P/Ns listed in paragraph (e)(2) of this AD, that exceeds its life limit. Use Tables I, II, III, and IV in paragraphs 3.D. through 3.G. in the Accomplishment Instructions in GE CT58 ASB No. SB 72-A0162, Revision 16, dated January 7, 2015, and paragraph 4.C., Appendix A of this GE CT58 ASB, to determine when to remove these parts. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (g) Related Information For more information about this AD, contact Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected]. (h) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) CT58 Alert Service Bulletin No. SB 72-A0162, Revision 16, dated January 7, 2015. (ii) Reserved. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, One Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; email: ge.com">[email protected]ge.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (5) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on September 30, 2015. Colleen M. D'Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015-25719 Filed 10-13-15; 8:45 am] BILLING CODE 4910-13-P
![61720 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations
(3) Will not affect intrastate aviation effective date of this AD, or at the next engine MA. For information on the availability of
in Alaska to the extent that it justifies shop visit, whichever occurs first: this material at the FAA, call 781–238–7125.
making a regulatory distinction, and (1) Remove the O-ring seal from the fuel (5) You may view this service information
(4) Will not have a significant manifold fitting, at the National Archives and Records
(2) Remove fuel manifold flow adapter, Administration (NARA). For information on
economic impact, positive or negative, the availability of this material at NARA, call
part numbers (P/Ns) 3059754–01, 3059757–
on a substantial number of small entities 01, and 3059760–01; and 202–741–6030, or go to: http://
under the criteria of the Regulatory (3) Install a fuel nozzle gasket and fuel www.archives.gov/federal-register/cfr/ibr-
Flexibility Act. manifold flow adapter that are eligible for locations.html.
List of Subjects in 14 CFR Part 39 installation, in accordance with paragraphs Issued in Burlington, Massachusetts, on
3.A, 3.B, and 3.C of P&WC SB No. PW100– September 22, 2015.
Air transportation, Aircraft, Aviation 72–21861, dated November 21, 2014.
safety, Incorporation by reference, Colleen M. D’Alessandro,
(f) Installation Prohibition Directorate Manager, Engine & Propeller
Safety.
After the effective date of this AD, fuel Directorate, Aircraft Certification Service.
Adoption of the Amendment manifold adapter, P/Ns 3059754–01, [FR Doc. 2015–25718 Filed 10–13–15; 8:45 am]
Accordingly, under the authority 3059757–01, and 3059760–01, and fuel BILLING CODE 4910–13–P
delegated to me by the Administrator, manifold gasket, P/N 3079354–01, are not
eligible for installation in any engine.
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as (g) Definition DEPARTMENT OF TRANSPORTATION
follows: For the purpose of this AD, an engine shop
Federal Aviation Administration
visit is the induction of an engine into the
PART 39—AIRWORTHINESS shop for maintenance involving the
DIRECTIVES separation of pairs of major mating engine 14 CFR Part 39
flanges. The separation of engine flanges [Docket No. FAA–2008–0808; Directorate
■ 1. The authority citation for part 39 solely for the purpose of transportation Identifier 2008–NE–18–AD; Amendment 39–
continues to read as follows: without subsequent engine maintenance does 18288; AD 2015–20–09]
Authority: 49 U.S.C. 106(g), 40113, 44701. not constitute an engine shop visit.
RIN 2120–AA64
(h) Alternative Methods of Compliance
§ 39.13 [Amended] (AMOCs) Airworthiness Directives; General
■ 2. The FAA amends § 39.13 by
The Manager, Engine Certification Office, Electric Company Turboshaft Engines
removing airworthiness directive (AD) FAA, may approve AMOCs to this AD. Use
2014–14–02], Amendment 39–17896 (79 the procedures found in 14 CFR 39.19 to AGENCY: Federal Aviation
FR 39958, July 11, 2014), and adding the make your request. You may email your Administration (FAA), DOT.
following new AD: request to: ANE-AD-AMOC@faa.gov. ACTION: Final rule.
2015–20–03 Pratt & Whitney Canada Corp.: (i) Related Information
Amendment 39–18281; Docket No. SUMMARY: We are superseding
(1) For more information about this AD, airworthiness directives (AD) 2001–18–
FAA–2013–1059; Directorate Identifier
contact Barbara Caufield, Aerospace 06 and AD 2008–22–16, for all General
2013–NE–36–AD.
Engineer, Engine Certification Office, FAA, Electric Company (GE) CT58 turboshaft
(a) Effective Date Engine & Propeller Directorate, 12 New
engines. AD 2001–18–06 and AD 2008–
This AD is effective November 18, 2015. England Executive Park, Burlington, MA
01803; phone: 781–238–7146; fax: 781–238– 22–16 required recalculating the lives of
(b) Affected ADs 7199; email: barbara.caufield@faa.gov. life-limited rotating parts using a
This AD replaces AD 2014–14–02, (2) Refer to MCAI Transport Canada AD repetitive heavy-lift (RHL) multiplying
Amendment 39–17896 (79 FR 39958, July 11, CF–2014–41, dated November 26, 2014, for factor and removal from service of parts
2014). related information. You may examine the that exceed the recalculated cyclic or
MCAI in the AD docket on the Internet at hourly life limit. This new AD would
(c) Applicability http://www.regulations.gov by searching for consolidate AD 2001–18–06 and AD
This AD applies to Pratt & Whitney Canada and locating it in Docket No. FAA–2013– 2008–22–16, and further reduce the life
Corp. (P&WC) PW120, PW121, and PW121A 1059.
capability of certain parts. This AD was
turboprop engines with post SB 21610 (j) Material Incorporated by Reference prompted by recalculation of life for
configuration; PW124B, PW127, PW127E,
and PW127F turboprop engines with post SB (1) The Director of the Federal Register parts installed on engines used in
21607 configuration; PW127E and PW127F approved the incorporation by reference Utility operations, and a reduced life for
turboprop engines with serial numbers (S/Ns) (IBR) of the service information listed in this compressor spools in all operations. We
PCE–EB0366 and earlier; PW127G turboprop paragraph under 5 U.S.C. 552(a) and 1 CFR are issuing this AD to prevent failure of
engines with S/Ns PCE–AX0275 and earlier; part 51. life-limited rotating parts, uncontained
and PW127M turboprop engines with S/Ns (2) You must use this service information part release, damage to the engine, and
PCE–ED0810 and earlier. as applicable to do the actions required by
damage to the aircraft.
this AD, unless the AD specifies otherwise.
(d) Unsafe Condition (i) Pratt & Whitney Canada Corp. Service DATES: This AD is effective November
This AD was prompted by reports of fuel Bulletin (SB) No. PW100–72–21861, dated 18, 2015.
seepage past the metal-to-metal sealing November 21, 2014. The Director of the Federal Register
surfaces of the fuel nozzle and fuel manifold (ii) Reserved. approved the incorporation by reference
flow adapter. We are issuing this AD to (3) For Pratt & Whitney Canada Corp. of a certain publication listed in this AD
prevent in-flight fuel leakage, engine fire, service information identified in this AD, as of November 18, 2015.
tkelley on DSK3SPTVN1PROD with RULES
damage to the engine, and damage to the contact Pratt & Whitney Canada Corp., 1000
ADDRESSES: For service information
airplane. Marie-Victorin Blvd., Longueuil, Quebec,
Canada, J4G 1A1; phone: 800–268–8000; fax: identified in this proposed AD, contact
(e) Compliance 450–647–2888; Web site: www.pwc.ca. General Electric Company, GE Aviation,
Comply with this AD within the (4) You may view this service information Room 285, One Neumann Way,
compliance times specified, unless already at FAA, Engine & Propeller Directorate, 12 Cincinnati, OH, 45215; phone: 513–
done. Within 1,500 flight hours after the New England Executive Park, Burlington, 552–3272; email:
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![61722 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations
the FAA amends 14 CFR part 39 as (3) Removal of Rotating Parts Used in Utility 202–741–6030, or go to: http://
follows: Operations Other Than Compressor Spools www.archives.gov/federal-register/cfr/ibr-
After the effective date of this AD, remove locations.html.
PART 39—AIRWORTHINESS from service any life-limited rotating part Issued in Burlington, Massachusetts, on
DIRECTIVES used in Utility operations, other than the September 30, 2015.
compressor spools with P/Ns listed in Colleen M. D’Alessandro,
■ 1. The authority citation for part 39 paragraph (e)(2) of this AD, that exceeds its
life limit as re-calculated per paragraph (e)(1) Directorate Manager, Engine & Propeller
continues to read as follows: Directorate, Aircraft Certification Service.
of this AD. Use Tables I, II, III, and IV in
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraphs 3.D. through 3.G. in the [FR Doc. 2015–25719 Filed 10–13–15; 8:45 am]
Accomplishment Instructions in GE CT58 BILLING CODE 4910–13–P
§ 39.13 [Amended] ASB No. SB 72–A0162, Revision 16, dated
January 7, 2015, and paragraph 4.D.,
■ 2. The FAA amends § 39.13 by: Appendix A of this GE CT58 ASB, to DEPARTMENT OF TRANSPORTATION
■ a. Removing airworthiness directives determine when to remove these parts.
(AD) 2001–18–06, Amendment 39– Federal Aviation Administration
(4) Removal of Rotating Parts Not Used in
12432 (66 FR 47575, September 13, Utility Operations Other Than Compressor
2001) (‘‘AD 2001–18–06’’); and AD Spools 14 CFR Part 39
2008–22–16, Amendment 39–15712 (73
After the effective date of this AD, remove [Docket No. FAA–2015–3224; Directorate
FR 63629, October 27, 2008) (‘‘AD from service any life-limited rotating part not Identifier 2015–CE–026–AD; Amendment
2008–22–16’’), and used in Utility operations, other than the 39–18290; AD 2015–20–11]
■ b. Adding the following new AD: compressor spools with P/Ns listed in
paragraph (e)(2) of this AD, that exceeds its RIN 2120–AA64
2015–20–09 General Electric Company:
life limit. Use Tables I, II, III, and IV in
Amendment 39–18288; Docket No. Airworthiness Directives; Schempp-
paragraphs 3.D. through 3.G. in the
FAA–2008–0808; Directorate Identifier
Accomplishment Instructions in GE CT58 Hirth Flugzeugbau GmbH Sailplanes
2008–NE–18–AD.
ASB No. SB 72–A0162, Revision 16, dated
(a) Effective Date January 7, 2015, and paragraph 4.C., AGENCY: Federal Aviation
Appendix A of this GE CT58 ASB, to Administration (FAA), Department of
This AD is effective November 18, 2015.
determine when to remove these parts. Transportation (DOT).
(b) Affected ADs ACTION: Final rule.
(f) Alternative Methods of Compliance
This AD replaces AD 2001–18–06 and AD (AMOCs)
2008–22–16. SUMMARY: We are adopting a new
The Manager, Engine Certification Office, airworthiness directive (AD) for
(c) Applicability FAA, may approve AMOCs for this AD. Use
Schempp-Hirth Flugzeugbau GmbH
This AD applies to all General Electric the procedures found in 14 CFR 39.19 to
make your request. You may email your Models Duo Discus and Duo Discus T
Company (GE) CT58–100–2, CT58–110–1,
request to: ANE-AD-AMOC@faa.gov. powered sailplanes. This AD results
CT58–110–2, CT58–140–1, and CT58–140–2
turboshaft engines. from mandatory continuing
(g) Related Information airworthiness information (MCAI)
(d) Unsafe Condition For more information about this AD, issued by an aviation authority of
This AD was prompted by recalculation of contact Christopher McGuire, Aerospace another country to identify and correct
life for parts installed on engines used in Engineer, Engine Certification Office, FAA, an unsafe condition on an aviation
Utility operations, and a reduced life for Engine & Propeller Directorate, 12 New
product. The MCAI describes the unsafe
compressor spools in all operations. We are England Executive Park, Burlington, MA
01803; phone: 781–238–7120; fax: 781–238– condition as excessive load on the air
issuing this AD to prevent failure of life-
7199; email: chris.mcguire@faa.gov. brake system. We are issuing this AD to
limited rotating parts, uncontained part
release, damage to the engine, and damage to require actions to address the unsafe
(h) Material Incorporated by Reference condition on these products.
the aircraft.
(1) The Director of the Federal Register DATES: This AD is effective November
(e) Compliance approved the incorporation by reference
18, 2015.
Do the actions required by this AD, unless (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register
already done. approved the incorporation by reference
part 51.
(1) Calculating Cyclic Life Consumption (2) You must use this service information of a certain publication listed in the AD
Re-calculate the cycles-since-new for all as applicable to do the actions required by as of November 18, 2015.
compressor spools, and for life-limited this AD, unless the AD specifies otherwise. ADDRESSES: You may examine the AD
rotating parts other than compressor spools (i) General Electric Company (GE) CT58 docket on the Internet at http://
used in Utility operations. Use paragraphs Alert Service Bulletin No. SB 72–A0162,
www.regulations.gov by searching for
3.A.(1) and 3.B.(1) in the Accomplishment Revision 16, dated January 7, 2015.
(ii) Reserved. and locating Docket No. FAA–2015–
Instructions of GE CT58 Alert Service
Bulletin (ASB) No. SB 72–A0162, Revision (3) For GE service information identified in 3224; or in person at Document
16, dated January 7, 2015, to perform the this AD, contact General Electric Company, Management Facility, U.S. Department
calculations. GE Aviation, Room 285, One Neumann Way, of Transportation, Docket Operations,
Cincinnati, OH 45215; phone: 513–552–3272; M–30, West Building Ground Floor,
(2) Removal of Compressor Spools email: aviation.fleetsupport@ge.com. Room W12–140, 1200 New Jersey
After the effective date of this AD, remove (4) You may view this service information Avenue SE., Washington, DC 20590.
compressor spools, part numbers (P/Ns) at FAA, Engine & Propeller Directorate, 12 For service information identified in
tkelley on DSK3SPTVN1PROD with RULES
5124T94G02, 6010T57G04, 6010T57G07, and New England Executive Park, Burlington,
this AD, contact Schempp-Hirth
6010T57G08 from service, before reaching MA. For information on the availability of
the life limits specified in paragraph 4.A., this material at the FAA, call 781–238–7125. Flugzeugbau GmbH, Krebenstrasse 25,
Appendix A, in GE CT58 ASB No. SB 72– (5) You may view this service information 73230 Kirchheim/Teck, Germany;
A0162, Revision 16, dated January 7, 2015, at the National Archives and Records telephone: +49 7021 7298–0; fax: +49
as re-calculated per paragraph (e)(1) of this Administration (NARA). For information on 7021 7298–199; email: info@schempp-
AD. the availability of this material at NARA, call hirth.com; Internet: http://
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Document Created: 2018-02-27 08:50:04
Document Modified: 2018-02-27 08:50:04
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 18, 2015. | |
| Contact | Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 80 FR 61720 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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